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PH II Harvard > ADY PROG 1 > Flashcards

ADY PROG 1 Flashcards

1
Q

Increasing the altitude decreases the rate of climb for a turboprop aircraft because excess power is decreased. Excess power is decreased because

A

The power required curve shifts up to the right and the power available curve shifts down

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2
Q

At sea level, doubling the true airspeed will generate

A

Twice as high an indicated airspeed and four times the dynamic pressure

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3
Q

What type of airfoil generates lift at zero angle of attack?

A

Positively cambered airfoil

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4
Q

Match the definition to the following term: Relative airflow
a. Direction of movement of atmosphere relative to the aircraft
b. Angle between the chord line and the relative airflow
c. Ratio of the wingspan to the chord line
d. Area of the wing’s shadow

A

Direction of movement of atmosphere relative to the aircraft

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5
Q

How does Newton’s Law of Acceleration relate to his explanation of lift production?
a. Downwash produces an equal and opposite reaction in the form of lift
b. The wing accelerates the surrounding air downward, creating downwash
c. The aircraft wing is an external force that upsets the equilibrium of the airflow
d. Downwash creates an area of low static pressure above the wing

A

The wing accelerates the surrounding air downward, creating downwash

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6
Q

What information do you need to calculate the wing area? Choose all that apply
a. Wingspan
b. Mean aerodynamic chord
c. Angle of attack
d. Mean camber line

A

a,b

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7
Q

Excess thrust is:

Equal to thrust available plus thrust required
Greates at low altitude
Equal to thrust available minus thrust required
Greatest at the maximum level flight speed

A

Greatest at low altitude

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8
Q

What will happen if you get too close to the lead’s wingtip when flying in echelon formation?

The lead will roll away from you
The lead will roll toward you
You will roll away from the lead
You will roll toward the lead

A

The lead will roll away from you

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9
Q

Angle of climb is directly proportional to the amount of:

Excess thrust
Rate of climb
Available power
Required power

A

Excess of thrust

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10
Q

At 200 knots indicated airspeed, doubling the equivalent flat plate area:

Will double the profile drag
Will double the total drag
Will increase the induced drag
Will increase the lift to drag ratio

A

Will double the profile drag

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11
Q

The aerodynamic limit of turning performance occurs when the aircraft has reached its maximum amount of lift, or its ______ for a particular airspeed

Load factor for that airspeed
Accelerated stalling speed
Structural limits for that airspeed
Manoeuvring speed

A

Accelerated stalling speed

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12
Q

How will increasing the altitude of a jet aircraft affect its range, endurance and the thrust available on the performance curves?

A

For the range : It will shift the thrust required curve to the right and considering the airframe, it will bring the tangent shallower, improving the range.

For the endurance, it will have no effect on the airframe component of a turbojet aircraft.

It will decrease the thrust available.

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13
Q

What is the most critical limitation to achieving maximum turn rate?

Maximum velocity
Maximum rate of climb
Maximum coefficient of lift
Maximum load factor

A

Maximum load factor

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14
Q

Boundary layer control produces a benefit to pilots because it can:

Increase lift at a given angle of attack
Decrease lift at a given angle of attack
Decrease the maximum lift coefficient
Increase the airfoil’s stalling angle of attack

A

Increase the airfoil’s stalling angle of attack

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15
Q

If you keep the wing area constant, but double the wingspan and double the aircraft weight, you will produce:

Less profile drag and less induced drag
The same profile drag and induced drag
More profile drag but less induced drag
Less profile drag and more induced drag

A

Same profile drag and same induced drag

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16
Q

What is the most critical limitation to achieving minimum turn radius?

Maximum velocity
Maximum coefficient of lift
Maximum load factor
Maximum rate of climb

A

Maximum coefficient of lift

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17
Q

The maximum angle of climb requires what for a jet aircraft?

A

Fly at L/Dmax

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18
Q

What is the minimum glide angle requirement?

A

Maximum Lift to Drag ratio.

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19
Q

In terms of the endurance of the aircraft, increasing the altitude will:

Have no effect upon the airframe consideration of a turbojet aircraft
Have no effect upon the engine consideration of a turbojet aircraft
Have no effect upon the airframe consideration of a turboprop aircraft
Have no effect upon the engine consideration of turboprop aircraft

A

Have no effect upon the airframe consideration of a turbojet aircraft

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20
Q

During the takeoff roll, the thrust force exceeds the sum of the:

Aerodynamic drag and friction force
Normal force and profile drag
Induced drag and profile drag
Friction force and normal force

A

Aerodynamic drag and friction force

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21
Q

Which of the folowing mechanisms is installed for improved dynamic stability, and NOT to reduce a pilot’s control forces?

Anti-servo balance tab
Internal balance
Balance tab
Mass balance

A

Mass balance

22
Q

The lift to drag ratio is inversely proportional to the gliding angle

True
False

A

True

23
Q

When you are in a post stall gyration, what effect does chasing the motion of the aircraft with the controls have?

Eventually, it brings your aircraft back under control
It makes the gyrations worse
It keeps the gyrations from becoming a steady spin
It has no effect

A

Makes the gyrations worse

24
Q

Profile drag is:

Inversely proportional to indicated airpseed
Directly proportional to span loading
Inversely proportional to true airspeed
Directly proportional to the square of true airspeed

A

Directly proportional to the square of true airspeed

25
Q

To maintain equilibrium in a steady state climb

The lift must be balanced by the component of weight which parallels the flight path
The thrust must be balanced by the drag as well as the component of weight which is perpendicular to the flight path
The thrust must be balanced by the drag as well as the component of weight which parallels the flight path
The thrust must be balanced by the drag

A

Thrust must be balanced by the drag as well as the component of weight which is parallel as the flight path.

26
Q

What helps to reduce the induced drag and consequently the power limit?

Increased velocity
Higher bank angle
Longer wingspan
Lower bank angle

A

Longer wingspan

27
Q

Increasing the altitude decreases the rate of climb for a turboprop aircraft because excess power is decreased. Excess power is decreased because

The power required curve shifts up to the left and the power available curve remains in the same place
The power required curve shifts up to the left and the power available curve shifts down
The power required curve shifts to the right (without moving up or down) and the power available curve shifts down
The power required curve shifts up to the right and the power available curve shifts down

A

The power required curve shifts up and to the right while the power available shifts down

28
Q

The maximum angle of climb requires:

The maximum ratio of excess thrust to weight
The maximum ratio of excess power to weight
The maximum thrust required
The sine of the climb angle to be a minimum

A

The maximum ratio of excess thrust to weight

29
Q

Aerodynamic braking predominantly uses which type of drag to slow the aircraft after touchdown?

Friction
Profile
Induced
Form

A

Profile

30
Q

What can you expect will happen to your aircraft’s performance if continually flying below manoeuvring speed? Choose all that apply
a. Turn rate decreases
b. Turn rate increases
c. Turn radius decreases
d. Turn radius increases

A

a,d

31
Q

What environmental and aircraft factors affect Specific Fuel Consumption and Brake Specific Fuel Consumption? Choose all that apply
a. Air inlet temperature
b. Air density
c. Velocity
d. Engine rotations per minute

A

a,d

32
Q

Steep turns are considered to be dangerous on approach because:

The angle of bank brings one wing closer to the ground
They increase the stall speed and sink rate
The decrease in the angle of attack can be dangerous
The added profile drag increases the stall speed

A

They increase the stall speed and sink rate

33
Q

At 200 knots indicated airspeed, doubling the equivalent flat plate area:

Will double the profile drag
Will double the total drag
Will increase the induced drag
Will increase the lift to drag ratio

A

Will double the profile drag

34
Q

Wing fence or wing notch

Reduces spanwise airflow at the wing tip, moving the boundary layer separation point closer to the wing root and preserving some lateral control at the ailerons
A vertical mini-airfoil that speeds up the air flowing through it. This increases the energy of the boundary layer and moves the separation point inboard
Placed near the root of the wing to physically disrupt the airflow, ensuring that the root stalls before any other part of the wing. The resultant turbulent air causes a buffeting sensation that you can feel, and thus serves as a stall warning
Controls the aircraft using an electronic interface rather than normal manual controls. This allows the aircraft computers to perform stabilizing functions without pilot input. It is the only modern design technique used to prevent stalls and spins. The rest are traditional technology

A

Reduces spanwise airflow at the wing tip, moving the boundary layer separation point closer to the wing root and preserving some lateral control at the ailerons

35
Q

Increasing the altitude of an aircraft attempting to glide for maximum range

Increases the optimum indicated airspeed and decreases the gliding angle
Increases the optimum indicated airspeed and maintains the same gliding angle
Increases the optimum true airspeed and increases the glide angle
Increases the optimum true airspeed and maintains the same gliding angle

A

Increases the optimum true airspeed and maintains the same gliding angle

36
Q

What happens if you get too close to the lead’s wingtip vortex when flying in echelon formation?

The lead will roll away from you
The lead will roll toward you
You will roll away from the lead
You will roll toward the lead

A

You will roll away from the lead

37
Q

Match the following term to the correct definition: Angle of climb

Converts kinetic to potential energy
Converts chemical energy to potential energy
Angle between horizon and the flight path
Vertical velocity

A

Angle between horizon and the flight path

38
Q

How can you reduce your sink rate?

Fly at the airspeed that produces the least amount of drag
Fly at L/D max
Fly at the airspeed that produces the least amount of power required
Fly out of a thermal

A

Fly at the airspeed that produces the least amount of power required

39
Q

Endurance airframe considerations have the same effects on aircraft as range airframe consideration

True
False

A

False

40
Q

Increasing the altitude:

Increases the thrust available from a turbojet aircraft
Increases the excess thrust
Decreases the thrust available from a turbojet aircraft
Increases the minimum thrust required

A

Decreases the thrust available from a turbojet aircraft

41
Q

What happens to endurance if you fly a turbojet aircraft above the tropopause?

Endurance remains the same as at the tropopause
Endurance is better than at the tropopause
Endurance is worse than at the tropopause
Endurance improves 5% for every 1,000 ft you climb above the tropopause

A

Endurance remains the same as at the tropopause

42
Q

Using power to control rate of descent on an approach is based upon the fact that:

Rate of descent is directly proportional to excess thrust
Rate of descent is directly proportional to excess horsepower
Rate of descent is directly proportional to weight
Rate of descent is inversely proportional to horsepower required

A

Rate of descent is directly proportional to excess horsepower

43
Q

What is the most critical limitation to achieving minimum turn radius?

Maximum velocity
Maximum coefficient of lift
Maximum load factor
Maximum rate of climb

A

Maximum coefficient of lift

44
Q

Angle of climb is directly proportional to the amount of:

Excess thrust
Rate of climb
Available power
Required power

A

Excess thrust

45
Q

Boundary layer control produces a benefit to pilots because it can:

Increase lift at a given angle of attack
Decrease lift at a given angle of attack
Decrease the maximum lift coefficient
Increase the airfoil’s stalling angle of attack

A

Increase the airfoil’s stalling angle of attack

46
Q

What will happen if you get too close to the lead’s wingtip when flying in echelon formation?

The lead will roll away from you
The lead will roll toward you
You will roll away from the lead
You will roll toward the lead

A

The lead will roll away from you

47
Q

In terms of the endurance of the aircraft, increasing the altitude will:

Have no effect upon the airframe consideration of a turbojet aircraft
Have no effect upon the engine consideration of a turbojet aircraft
Have no effect upon the airframe consideration of a turboprop aircraft
Have no effect upon the engine consideration of turboprop aircraft

A

No effect considering the airframe of a turbojet aircraft

48
Q

What is the most critical limitation to achieving maximum turn rate?

Maximum velocity
Maximum rate of climb
Maximum coefficient of lift
Maximum load factor

A

Maximum load factor

49
Q

A turbojet’s thrust

Is constant with speed, while its power increases in direct proportion to velocity
Is more affected by speed than a turbofan
Is constant with RPM changes
Increases in direct proportion to the RPM

A

Is constant with speed, while its power increases in direct proportion to velocity

50
Q
A

PH II Harvard (7 decks)

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